Projectile



"TCU-Z400 Dec. 3, 1946. c. L. EKsERGIAN 2,412,134

PROJECTILE Filed F'Fb. 12. 1944 7 l JNVENTOR CaroluS LrELerq Lan.

BY l ATTORNEY Adrical elements 9 of combustible material.

Patented Dec. 3, 1946 PROJ ECTILE Carolus L. Eksergian, Detroit, Mich.,assgnor, by mesne assignments, to the United States of America, asrepresented by the Secretary of War Application February 12, 1944,Serial No. 522,037

This invention relates to reaction propulsion devices, more particularlyto projectiles and the like of the so-called rocket type.

Projectiles embodying a casing which encloses a reaction propulsioncharge that discharges peripherally from the casing have previously beenproposed, and the present invention is ydirected primarily to this typeof projectile.

One of the objects of the present invention is to provide an improvednozzle or jet arrangement in a rocket type projectile which iseconomical to manufacture and in which means is provided for adjustingthe area of the nozzle passage to provide for desired ranges of theprojectile through Variation in the propelling pressure of theexhausting gases.

Another object is to provide an improved multijet rocket device in whichseparate propelling charges may be utilized.

With the above and other objects in View which will be 'apparent fromthe following description to those skilled in the art to which theinvention appertains, the present invention consists in certain featuresof construction and combinations of parts to be hereinafter describedwith reference to the accompanying drawing, and then claimed.

In the drawing which illustrates a suitable embodiment of the invention:

Figure 1 is a side elevation of the projectile to I" which thearrangement of the present invention is applied;

Figure 2 is an enlarged section of that portion of the projectile whichis disposed within broken outline 2 of Figure 1, and

Figures 3 and 4 are transverse sections respectively taken substantiallyon the lines 3-3 and 4-4 of Figure 2.

Referring to the drawing, the projectile selected for illustrationcomprises a rearward tubular casing 5, a forward tubular casing v6 ofgreater diameter than the rearward casing 5 and a nose portion 'I whichmay contain an explosive charge, or are or chemical charge and the like(not shown). Suitable stabilizing fins 8 are carried by the trailing endof the casing 5.

Each of the casings contains a reaction propulsion charge in the form ofa number of cylilr- T e elements '9 are supported in circumferentiallyspaced relation on a suitable cage Il) concentrically arranged withinthe casing. The particular manner of supporting the cage I forms no partof the present invention and therefore is not shown in detail.

Claims. (Cl. 60-35.6)

Extending axially within the casings 5 and 6 is a tubular member IIsupported at its forward end by the nose portion 'I and at its rearwardend by the rearward end of the casing 5, as indicated in dotted outlinein Figure 1.

In accordance with the present invention, a separate jet or Venturipassage is provided for each reaction propulsion charge comprised of thecylindrical elements 9. To this end, a tubular sleeve I2 surrounds thetube II, and surrounds the sleeve I2 and secured thereto by silversolder I3 or by any other suitable method, are forward and rearwardannular elements I4 and I5, respectively, the element I4 beingperipherally threaded to the internal wall of casing 6 and the elementI5 being peripherally threaded to the internal wall of casing 5. Theradial walls or webs of the elements I4 and I5 are of spider formationto provide the element I4 with openings |6 and the element|5 withopenings I'I.

Interposed between the annular elements I4 and I5 and surrounding thesleeve I2 is an annular member I8 having an integral circumferentialrearwardly and outwardly extending wall I9. As will be seen in Figure 2,this wall is of conical formation and projects rearwardly and outwardlybetween the adjacent spaced ends of the casings `5 and 6.

Threaded to the end of the casing 5 is an annular ring 20, and similarlythreaded to the end of the casing 6 is an annular ring 2|. ward end ofthe ring 20 is tapered at 22, as shown in Figure 22, and this taperedsurface 2 together with the inner surface 23 of the wall IES provides .aVenturi passage 2-4 communicating with the easing i5 through theopenings I1 for the exhaust of the products of combustion of thereaction propulsion charge comprised of the rearward elements 9. Theinner surface of the ring 2| is also contoured at 25 `to provide withthe outer surface 26 of the conical wall I9 a Venturi passage 2'I incommunication with the casing 6 through the openings I6 for the exhaustof the products of combustion of the reaction propulsion charge locatedwithin the casing 6.

There is thus provided continuously annular Venturi passagesy 24 and 2'Iseparated by the single wall |9,the one communicating with one casingand the other with the other casing.

The annular rings 20 and 2| are threadedly adjustable on the ends of thecasings so that the areas of the Venturi passages 24 and 26,respectively, may be adjusted to provide for a predetermined propellingpressure. Suitable set The for- 3 screws 28 may be provided to lock therings 20 and 2| in adjusted position.

It is to be noted that through the medium of the annular rings I4 and I5and the annular sleeve I2 a rigid connection is provided between theadjacent ends of the two casings, despite the fact that these ends arecompletely separated. In fact the forward end of the rearward casing isrigidly supported from the rearward end of the forward casing.

The connection between the twol casings and the particular constructionof the Venturi passage provides an arrangement which, although simple inconstruction, can be economically manufactured.

Various changes may be made in the arrangement and detailed constructionof the parts described without departing from the 'spirit and substanceof the invention, the scope of which is defined by the appended claims.

What is claimed is:

1. In a reaction propulsion device, a pair of coaxial tubular casingshaving their adjacent ends in spaced apart relation, each being arrangedto \contain agninbnvstuilgleq reaction propulsion charge each having anaxially apertured elementedwithin the end thereof 4which is adjacent theother casing, rigid means within said casings rigidly secured to saidapertured elements, whereby to supportv ne casing from the other, and anannular wall extending at an acute angle to the axis of said casingthrough the space between said adjacent ends in spaced relation withrespect to each of said `ends, said wall providng with each of said endsa peripherally continuous discharge passage.

2. In a reaction propulsion device, a pair of coaxial tubular casingshaving their adjacent ends in spacemapart relation, each being arrangedto contain a combustible reaction :propulsion charge each having anaxially apertured element secured within the end thereof which isadjacent the other casing,vmeans within said casings rigidly secured vtosaid apertured elements to support one casing from the other, and anannular wall extending at an acute angle to the axis of said casingthrough the space between said adjacent ends in spaced relation withrespect to each of said ends, said wall providing with each of said endsa peripherally continuous discharge passage, said wall extending frombetween said apertured elements and preventing the ow of the products ofcombustion of the charge in each casing from entering the other casing.

3. In a reaction propulsion device, a pair of coaxial tubular casingshaving their adjacent ends in sgacednapart relation, each being arrangedto contain La combustible reaction propulsion charge, each casing havingan axially apertured element secured within the end thereof which isadjacent an end of the other casing, rigid means within said casingsrigidly secured to said apertured elements, whereby .to support onecasing from the other, and an annular wall extending at an acute angleto the axis of said casing through the space between said adjacent endsin spaced relation with respect to each of said ends, each of said endsand the adjacent surface of said wall being contoured to dene acircumferentially continuous Venturi passage,

4. In a reaction propulsion device, a pair of coaxial tubular casingshaving their adjacent ends in sp ed apartmrelation, each being arrangedto con`a'n'cninbustible reaction propulsion @haargg each having" anaxially apertured elementI :secured within the end thereof which isadjacent the other casing, rigid means within said casings rigidlysecured to said apertured elements, whereby to support one casing fromthe other, and an annular wall extending at an acute angle to the axisof said casing through the space between said adjacent ends in spacedrelation with respect to each of said ends, each of said adjacent endshaving an annular ring threaded thereto, each of said rings and theadjacent surface of said wall being contoured to define a Venturi passagand said rings being threadably adjustable on said casings to alter theareas of said Venturi passages whereby to vary the pressures at whichthe gases resulting from the burning of the propulsion charges willexhaust from said Venturi passages.

5. In a reactionv propulsion device, a pair of coaxial tubular casingshaving their adjacent ends in space part-relation, each being arrangedto contain a combustible reaction propulsion charge, each casing havingan axially apertured element secured within the end thereof which isadjacent an end of the other casing, a member extending between saidelements and being rigidly secured thereto, and a sleeve-like membersurrounding said first mentioned member and extending between saidelements, said sleeve-like member having a circumferential annular walloutwardly therefrom at an acute angle between said adjacent ends, saidwall being spaced from both said ends and providing continuous annularpassages therewith, the one for the discharge of the products ofcombustion of the charge in one'casing and the other for the dischargeof the products of combustion of the charge in the other casing.

CAROLUS L. EKSERGIAN.

